EP0391327A1 - Method and apparatus for grounding multi-layer insulations, especially for space structures - Google Patents
Method and apparatus for grounding multi-layer insulations, especially for space structures Download PDFInfo
- Publication number
- EP0391327A1 EP0391327A1 EP90106327A EP90106327A EP0391327A1 EP 0391327 A1 EP0391327 A1 EP 0391327A1 EP 90106327 A EP90106327 A EP 90106327A EP 90106327 A EP90106327 A EP 90106327A EP 0391327 A1 EP0391327 A1 EP 0391327A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- layer
- layers
- layer insulation
- underlying structure
- insulation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000009413 insulation Methods 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 title abstract description 10
- 229910052751 metal Inorganic materials 0.000 claims description 13
- 239000002184 metal Substances 0.000 claims description 11
- 239000004020 conductor Substances 0.000 claims description 2
- 230000004224 protection Effects 0.000 abstract description 5
- 238000010276 construction Methods 0.000 abstract description 2
- 239000000853 adhesive Substances 0.000 description 10
- 230000001070 adhesive effect Effects 0.000 description 10
- 238000000576 coating method Methods 0.000 description 9
- 239000011248 coating agent Substances 0.000 description 8
- 238000004026 adhesive bonding Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 239000000835 fiber Substances 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 229920000728 polyester Polymers 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- 239000004952 Polyamide Substances 0.000 description 1
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 1
- 239000004809 Teflon Substances 0.000 description 1
- 229920006362 Teflon® Polymers 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 229910052732 germanium Inorganic materials 0.000 description 1
- GNPVGFCGXDBREM-UHFFFAOYSA-N germanium atom Chemical compound [Ge] GNPVGFCGXDBREM-UHFFFAOYSA-N 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- AMGQUBHHOARCQH-UHFFFAOYSA-N indium;oxotin Chemical compound [In].[Sn]=O AMGQUBHHOARCQH-UHFFFAOYSA-N 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 229920002647 polyamide Polymers 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K9/00—Screening of apparatus or components against electric or magnetic fields
- H05K9/0007—Casings
- H05K9/002—Casings with localised screening
- H05K9/0039—Galvanic coupling of ground layer on printed circuit board [PCB] to conductive casing
Definitions
- the present invention relates to the field of grounding against the danger of electrostatic discharges (ESD) on multi-layer installations (MLI) used as heat protection of space satellites and structures.
- grounding system of multi-layer insulations used as thermal protection for satellites and space structures is usually developed in such a manner as to have one or more points of electrical connection with the underlying structure in order to avoid the accumulation of electrostatic charges; these are potential causes of electrostatic discharges (ESD) which may damage or alter the characteristics of the multi-layer insulation itself and may create electrical interference and partially or completely damage the electronic apparatus present on board the space structure.
- ESD electrostatic discharges
- the present techniques for protection against ESD employ more than one grounding point on each MLI, which points are however, different from the points of attachment of the MLI to the underlying structure.
- a metallic material which may be a strip of aluminum sheet or thin washers of metal or of electroconductive rubber.
- Another metallic element which may be a strip of metal sheet or a metal cable or wire is therefore used to connect each grounding point of the MLI, either to another grounding point on the contiguous MLI or on the underlying structure or on the structure of the satellite itself.
- Said method provides that each layer of the MLI is in electrical contact with the others and that all the layers are in electrical contact with the underlying structure by one or more points of mechanically attaching the MLI to said underlying structure.
- a multi-layer insulation 12 electrically to an underlying structure 1 which is also electrically conductive, such as a metallic structure or a composite material with carbon fibers or metal matrix.
- This multi-layer insulation 12 is normally used as passive thermal protection on space structures or satellites.
- the electrical connection between the multi-layer insulation 12 and the underlying structure 1 is effected by the same system of mechanical attachment as anchors the MLI 12 to the said structure 1.
- This system of attachment consists in part of hooks 2 and in part of piles 3, of which the attachment system is formed like that of the Velcro LTD system, commonly known by the expression "hook & pile.”
- Both the hook part 2 and the pile part 3 is made of electrically conductive material such as nylon or polyester metalized with silver, copper or aluminum.
- the hook element 2 is glued on to the underlying structure 1 using a conductive adhesive 19, which is readily obtainable on the market.
- the pile part 3 and the hook part 2 may also be reversed, gluing the pile part 3 on the structure 1 and arranging the hook part 2 on the MLI 12.
- conductive adhesives do not generally have great adhesive strength, they are preferably not used for structural gluings.
- the conductive adhesive material 19 is used only in the central part of the gluing of the hook part 2 to the underlying structure 1.
- the outer part of the gluing 4 is effected by the use of a structural adhesive of greater adhesive strength.
- the hook part 2 of the attachment system can be connected to the underlying structure 1 by a metal rivet or a screw or by any type of mechanical and metallic attachment system, whether stationary or removable, or by the combination of a mechanical and an adhesive system.
- the outer layer 7 of the multi-layer insulation 12 must have applied to it a transparent conductive coating 13 such as that formed of ITO (indium tin oxide) or germanium on the outer surface (that facing space) and a vacuum deposited aluminum coating (VDA) 14 on the surface facing the inside (Fig. 2).
- a transparent conductive coating 13 such as that formed of ITO (indium tin oxide) or germanium on the outer surface (that facing space) and a vacuum deposited aluminum coating (VDA) 14 on the surface facing the inside (Fig. 2).
- Suitable materials with which to produce the outer layer 7 can be a film of polyamides or polyesters or Teflon. Such films are available in various thicknesses with different thermo-optical properties.
- the outer layer 7 is perforated as by holes 9.
- the holes 9 are preferably made before the application of the outer conductive coating 13 and of the coating of VDA 14.
- the size of these holes 9 and their pitch are not critical provided that the number of holes is such as to assure a certain redundance for the system of grounding the multi-layer insulation 12.
- the application of the two metal coatings (that of ITO 13 and that of VDA 14) produces an interconnection 11 on the wall of each hole, permitting electrical continuity between the front coated with ITO 13 and the surface facing the inside which is coated with VDA 14.
- the intermediate layers are also made of plastic material, but not necessarily the same material as that of which the outer layer is made, nor necessarily of the same thickness.
- the intermediate layers 6 have a coating of VDA 14 on both surfaces; they also must have a number of holes 15, interconnected by the deposition after the drilling of the film, of the VDA coating on the wall of the hole, which is sufficiently high to assure the redundance of the total grounding system of the MLI 12 (see Figs. 3 and 4).
- Each intermediate layer 6 should not be in contact with the adjacent ones in order to minimize the heat exchanges by conduction which would decrease the efficiency of the MLI 12.
- sheets of heat insulation 5 the latter preferably consisting of a light, thin plastic fiber woven in such a manner as to form a network or continuous layer with a plurality of holes.
- This thermal insulating function can also be performed by the intermediate layers themselves, if arranged in such a manner as to minimize the areas of mutual contact; this can be obtained by using intermediate layers which are metalized on both surfaces, pleated or made in relief.
- This thermal insulation 5, if used, will be eliminated around the point of attachment of the multi-layer insulation 12 to the underlying structure 1 in such a manner that when the layers are compressed together, by a metal clamp 10, a metallic system which may be a rivet 17 with a washer 18, by means of a sewing thread which is also electrically conductive, such as graphite or metal or metalized organic fiber or some combination of such means for compressing, there is electric continuity between the conductive coating of the outer layer 13 and the inner layer 8.
- the entire multi-layer insulation 12 can transmit the electrostatic charges to the hook part 2 of the attachment system and therefore, through the conductive adhesive 19 applied between the hook part 2 of the attachment system and the structure 1 it is possible to connect all the layers of the multi-layer insulation 12 to the underlying structure 1 (see Fig. 1).
- the inner layer 8 may be desirable that the inner layer 8 has the conductive coating of VDA 14 only on the surface which faces the other layers and in such case the electric connection between the outer layer 13 and the outer surface of the inner layer 20 is interrupted.
- a metallic or mechanical attachment system 17 which may be a screw or a rivet 17 combined with a washer 18.
- This attachment system 17 of mechanical type is in contact with the rear surface of each layer if a cut of slit type 16 is made on each layer and the mechanical attachment element 17 is pushed through this slit 16.
- the mechanical attachment system 17 is locked together to the washer 18, the electrical contact will again be assured between the hook part 3 of the hook/pile attachment system and the outer layer 13 (see Figs. 5, 6, 7, 8).
- several mechanical attachment systems 17 and washers 18 may be used if desired.
- the present invention describes a method of effecting the grounding of multi-layer insulations assigned to the passive thermal control of satellites or space structures.
- each layer of the multi-layer insulation is in electrical contact with the other layers and all the layers are electrically connected with the underlying structure which is also electrically conductive.
- the multi-layer insulation is electrically connected to the underlying structure by the said attachment system of the multi-layer insulation of the structure.
Landscapes
- Engineering & Computer Science (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Production Of Multi-Layered Print Wiring Board (AREA)
- Building Environments (AREA)
- Laminated Bodies (AREA)
- Coupling Device And Connection With Printed Circuit (AREA)
- Insulating Bodies (AREA)
- Paper (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
- The present invention relates to the field of grounding against the danger of electrostatic discharges (ESD) on multi-layer installations (MLI) used as heat protection of space satellites and structures.
- In the course hereof, for convenience, acronyms known to specialists in the field will be used. We will not provide the explicit meanings thereof insofar as they are now accepted in the specific terminology. The grounding system of multi-layer insulations used as thermal protection for satellites and space structures is usually developed in such a manner as to have one or more points of electrical connection with the underlying structure in order to avoid the accumulation of electrostatic charges; these are potential causes of electrostatic discharges (ESD) which may damage or alter the characteristics of the multi-layer insulation itself and may create electrical interference and partially or completely damage the electronic apparatus present on board the space structure.
- The present techniques for protection against ESD employ more than one grounding point on each MLI, which points are however, different from the points of attachment of the MLI to the underlying structure.
- At each grounding point all the layers which form the multi-layer insulation (the outside one which faces space, the inside one which faces the structure and the intermediate ones) are in contact generally through a metallic material which may be a strip of aluminum sheet or thin washers of metal or of electroconductive rubber. Another metallic element which may be a strip of metal sheet or a metal cable or wire is therefore used to connect each grounding point of the MLI, either to another grounding point on the contiguous MLI or on the underlying structure or on the structure of the satellite itself.
- Such systems of effecting the grounding are complicated and require a large number of points in order to obtain the necessary reliability on each MLI; they are furthermore very laborious to construct and therefore increase the cost of construction, usually adding undesired weight to the MLI and therefore to the satellite or space structure. These problems are solved by the method of grounding which forms the object of the present invention.
- Said method provides that each layer of the MLI is in electrical contact with the others and that all the layers are in electrical contact with the underlying structure by one or more points of mechanically attaching the MLI to said underlying structure.
- The invention will now be described with reference to one embodiment which is at present preferred by the inventor, and is indicated by way of illustration and not of limitation with reference to the accompanying drawing in which:
- Fig. 1 diagrammatically shows the type of multi-layer insulation in accordance with the present invention;
- Fig. 2 is an enlarged view of the outer layer of the multi-layer insulation;
- Fig. 3 is an enlarged view of an intermediate layer of the multi-layer insulation;
- Fig. 4 is an enlarged view of the inner layer of the multi-layer insulation;
- Fig. 5 is a plan view of slit cut made on the multi-layer insulation;
- Fig. 6 is an exploded perspective of a metal rivet which penetrates through the slit cut made in the multi-layer insulation, and a washer which will be fastened on the rivet in contact with the multi-layer insulation;
- Fig. 7 is an exploded perspective view which shows the technique of gluing, both structural and electric, of half of the mechanical attachment system, with hooks and pile, to the underlying structure;
- Fig. 8 is an enlarged section of the area of attachment of the MLI, the arrangement of the layers which form the MLI when the electric contact is assured by the rivet and the metallic washer.
- Returning now to Fig. 1, the preferred means for grounding shown makes it possible to connect a
multi-layer insulation 12 electrically to anunderlying structure 1 which is also electrically conductive, such as a metallic structure or a composite material with carbon fibers or metal matrix. - This
multi-layer insulation 12 is normally used as passive thermal protection on space structures or satellites. - The electrical connection between the
multi-layer insulation 12 and theunderlying structure 1 is effected by the same system of mechanical attachment as anchors theMLI 12 to thesaid structure 1. This system of attachment consists in part ofhooks 2 and in part of piles 3, of which the attachment system is formed like that of the Velcro LTD system, commonly known by the expression "hook & pile." - Both the
hook part 2 and the pile part 3 is made of electrically conductive material such as nylon or polyester metalized with silver, copper or aluminum. Thehook element 2 is glued on to theunderlying structure 1 using aconductive adhesive 19, which is readily obtainable on the market. - The pile part 3 and the
hook part 2 may also be reversed, gluing the pile part 3 on thestructure 1 and arranging thehook part 2 on theMLI 12. - Since conductive adhesives do not generally have great adhesive strength, they are preferably not used for structural gluings. Preferably, the conductive
adhesive material 19 is used only in the central part of the gluing of thehook part 2 to theunderlying structure 1. The outer part of thegluing 4 is effected by the use of a structural adhesive of greater adhesive strength. - Alternatively, the use of a conductive adhesive of satisfactory mechanical properties permits gluing the conductive adhesive alone.
- The
hook part 2 of the attachment system can be connected to theunderlying structure 1 by a metal rivet or a screw or by any type of mechanical and metallic attachment system, whether stationary or removable, or by the combination of a mechanical and an adhesive system. - The
outer layer 7 of themulti-layer insulation 12 must have applied to it a transparentconductive coating 13 such as that formed of ITO (indium tin oxide) or germanium on the outer surface (that facing space) and a vacuum deposited aluminum coating (VDA) 14 on the surface facing the inside (Fig. 2). - Suitable materials with which to produce the
outer layer 7 can be a film of polyamides or polyesters or Teflon. Such films are available in various thicknesses with different thermo-optical properties. Theouter layer 7 is perforated as byholes 9. Theholes 9 are preferably made before the application of the outerconductive coating 13 and of the coating of VDA 14. The size of theseholes 9 and their pitch are not critical provided that the number of holes is such as to assure a certain redundance for the system of grounding themulti-layer insulation 12. - The application of the two metal coatings (that of ITO 13 and that of VDA 14) produces an
interconnection 11 on the wall of each hole, permitting electrical continuity between the front coated withITO 13 and the surface facing the inside which is coated with VDA 14. - The presence of these holes, furthermore, performs the function of the removal of the air enclosed between the
multi-layer insulation 12 and theunderlying structure 1 when, during the launching phase of satellites or space structures, one passes from ambient pressure (760mm Hg at sea level) to absolute vacuum. - The intermediate layers are also made of plastic material, but not necessarily the same material as that of which the outer layer is made, nor necessarily of the same thickness. The
intermediate layers 6 have a coating ofVDA 14 on both surfaces; they also must have a number ofholes 15, interconnected by the deposition after the drilling of the film, of the VDA coating on the wall of the hole, which is sufficiently high to assure the redundance of the total grounding system of the MLI 12 (see Figs. 3 and 4). Eachintermediate layer 6 should not be in contact with the adjacent ones in order to minimize the heat exchanges by conduction which would decrease the efficiency of theMLI 12. - This is obtained by interposing sheets of
heat insulation 5, the latter preferably consisting of a light, thin plastic fiber woven in such a manner as to form a network or continuous layer with a plurality of holes. - This thermal insulating function can also be performed by the intermediate layers themselves, if arranged in such a manner as to minimize the areas of mutual contact; this can be obtained by using intermediate layers which are metalized on both surfaces, pleated or made in relief.
- This
thermal insulation 5, if used, will be eliminated around the point of attachment of themulti-layer insulation 12 to theunderlying structure 1 in such a manner that when the layers are compressed together, by ametal clamp 10, a metallic system which may be arivet 17 with awasher 18, by means of a sewing thread which is also electrically conductive, such as graphite or metal or metalized organic fiber or some combination of such means for compressing, there is electric continuity between the conductive coating of theouter layer 13 and theinner layer 8. - Through the pile part 3 of the hook/pile attachment system, the entire
multi-layer insulation 12 can transmit the electrostatic charges to thehook part 2 of the attachment system and therefore, through theconductive adhesive 19 applied between thehook part 2 of the attachment system and thestructure 1 it is possible to connect all the layers of themulti-layer insulation 12 to the underlying structure 1 (see Fig. 1). For some multi-layer insulations it may be desirable that theinner layer 8 has the conductive coating of VDA 14 only on the surface which faces the other layers and in such case the electric connection between theouter layer 13 and the outer surface of theinner layer 20 is interrupted. - Since the
metal clamp 10 or the conductive wire may not be able to effect sufficient electric contact, use may be made of a metallic ormechanical attachment system 17 which may be a screw or arivet 17 combined with awasher 18. - This
attachment system 17 of mechanical type is in contact with the rear surface of each layer if a cut of slit type 16 is made on each layer and themechanical attachment element 17 is pushed through this slit 16. When themechanical attachment system 17 is locked together to thewasher 18, the electrical contact will again be assured between the hook part 3 of the hook/pile attachment system and the outer layer 13 (see Figs. 5, 6, 7, 8). Of course, severalmechanical attachment systems 17 andwashers 18 may be used if desired. - The present invention describes a method of effecting the grounding of multi-layer insulations assigned to the passive thermal control of satellites or space structures.
- In the method presented, each layer of the multi-layer insulation is in electrical contact with the other layers and all the layers are electrically connected with the underlying structure which is also electrically conductive.
- The multi-layer insulation is electrically connected to the underlying structure by the said attachment system of the multi-layer insulation of the structure.
Claims (2)
both faces of the other layers (6) (8) being electrically conductive, said both faces of each other layer being electrically connected by the presence of holes (9) the walls of which are conductive;
an underlying structure, means for attaching the multi-layer insulation (12) to the underlying structure (1) including a hook and pile fastener (2 and 3) of electrically conductive material;
one part of the hook and pile fastener being electrically conductively attached to the multi-layer insulation (12) and the other part being electrically conductively attached to the underlying structure (1).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT4780889 | 1989-04-03 | ||
IT8947808A IT1231457B (en) | 1989-04-03 | 1989-04-03 | PROCEDURE FOR THE REALIZATION OF THE MASSING OF MULTI-LAYER INSULATIONS (THERMAL BLANKETS) FOR SPATIAL APPLICATIONS |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0391327A1 true EP0391327A1 (en) | 1990-10-10 |
EP0391327B1 EP0391327B1 (en) | 1994-08-31 |
Family
ID=11262645
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP90106327A Expired - Lifetime EP0391327B1 (en) | 1989-04-03 | 1990-04-03 | Method and apparatus for grounding multi-layer insulations, especially for space structures |
Country Status (6)
Country | Link |
---|---|
US (1) | US5111354A (en) |
EP (1) | EP0391327B1 (en) |
AT (1) | ATE110925T1 (en) |
CA (1) | CA2013682A1 (en) |
DE (1) | DE69011920T2 (en) |
IT (1) | IT1231457B (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0584550A1 (en) * | 1992-08-28 | 1994-03-02 | Dornier Gmbh | Clip |
FR2695290A1 (en) * | 1992-09-02 | 1994-03-04 | Philips Electronics Nv | Circuit for high frequencies, and method for making it |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5457610A (en) * | 1993-06-01 | 1995-10-10 | Motorola, Inc. | Low profile mechanical interconnect system having metalized loop and hoop area |
US5494755A (en) * | 1994-06-08 | 1996-02-27 | Lockheed Missiles & Space Co., Inc. | Passive intermodulation products (PIM) free tape |
US6981671B1 (en) * | 2001-03-28 | 2006-01-03 | The United States Of America As Represented By The Secretary Of The Air Force | Airframe structure-integrated capacitor |
US7014143B2 (en) * | 2002-10-11 | 2006-03-21 | The Boeing Company | Aircraft lightning strike protection and grounding technique |
US9944445B2 (en) * | 2015-05-14 | 2018-04-17 | Gerald C Altomare | Apparatus and method of embedding articles within reclosable fastener systems |
EP3339189B1 (en) | 2016-12-23 | 2020-06-17 | Airbus Defence and Space GmbH | Electrically connecting multi-layer insulation blankets |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE7705759U1 (en) * | 1977-02-25 | 1977-06-02 | Robert Bosch Gmbh, 7000 Stuttgart | Enclosures for electronic devices |
DE2833480A1 (en) * | 1978-07-31 | 1980-02-14 | Siemens Ag | Circuit board for communication equipment - consists of foil with holes broken in it for component leads soldered to foil edges |
US4739453A (en) * | 1986-03-20 | 1988-04-19 | Kabushiki Kaisha Toshiba | Shielding apparatus for a printed circuit board |
US4768286A (en) * | 1986-10-01 | 1988-09-06 | Eastman Christensen Co. | Printed circuit packaging for high vibration and temperature environments |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3857994A (en) * | 1973-04-09 | 1974-12-31 | Nat Telephone Supply Co | Non-corrosive cable shield bond |
US4329731A (en) * | 1980-04-30 | 1982-05-11 | Communications Satellite Corporation | Discharge suppressing dielectric film for use on spacecraft surfaces |
US4623951A (en) * | 1982-05-24 | 1986-11-18 | Hughes Aircraft Company | Electrically conductive composite structure |
-
1989
- 1989-04-03 IT IT8947808A patent/IT1231457B/en active
-
1990
- 1990-03-30 US US07/502,434 patent/US5111354A/en not_active Expired - Fee Related
- 1990-04-03 AT AT90106327T patent/ATE110925T1/en not_active IP Right Cessation
- 1990-04-03 DE DE69011920T patent/DE69011920T2/en not_active Expired - Fee Related
- 1990-04-03 CA CA002013682A patent/CA2013682A1/en not_active Abandoned
- 1990-04-03 EP EP90106327A patent/EP0391327B1/en not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE7705759U1 (en) * | 1977-02-25 | 1977-06-02 | Robert Bosch Gmbh, 7000 Stuttgart | Enclosures for electronic devices |
DE2833480A1 (en) * | 1978-07-31 | 1980-02-14 | Siemens Ag | Circuit board for communication equipment - consists of foil with holes broken in it for component leads soldered to foil edges |
US4739453A (en) * | 1986-03-20 | 1988-04-19 | Kabushiki Kaisha Toshiba | Shielding apparatus for a printed circuit board |
US4768286A (en) * | 1986-10-01 | 1988-09-06 | Eastman Christensen Co. | Printed circuit packaging for high vibration and temperature environments |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0584550A1 (en) * | 1992-08-28 | 1994-03-02 | Dornier Gmbh | Clip |
FR2695290A1 (en) * | 1992-09-02 | 1994-03-04 | Philips Electronics Nv | Circuit for high frequencies, and method for making it |
EP0586010A1 (en) * | 1992-09-02 | 1994-03-09 | Philips Electronique Grand Public | High frequency circuit device and method for making the same |
Also Published As
Publication number | Publication date |
---|---|
ATE110925T1 (en) | 1994-09-15 |
DE69011920T2 (en) | 1995-05-04 |
EP0391327B1 (en) | 1994-08-31 |
US5111354A (en) | 1992-05-05 |
IT1231457B (en) | 1991-12-07 |
DE69011920D1 (en) | 1994-10-06 |
IT8947808A0 (en) | 1989-04-03 |
CA2013682A1 (en) | 1990-10-03 |
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Legal Events
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